125 results about "Airborne system" patented technology

The embodiment of the invention provides a modeling method and device for an airborne system function architecture model, computer equipment and a medium, and relates to the technical field of aviation architecture design, the method comprises the following steps: inputting a design requirement document into an airborne large language model, and in the large language model, under the structural constraint of an airborne system knowledge graph, establishing a design requirement document; the method comprises the following steps: extracting a logical relationship between entities required by airborne system modeling from a design demand document, screening a corresponding airborne meta-model according to the extracted logical relationship between the entities, and constructing a demand graph; constructing and outputting a text model of a concept scene, a text model of a task scene, a text model of a system function, a text model of a logic architecture and a text model of a physical architecture of the airborne system based on the demand graph; and inputting each text model into a system modeling language modeling terminal for visualization to obtain a multi-level functional architecture model of the airborne system. According to the scheme, the modeling efficiency, consistency and normalization are improved.

The invention discloses a gas turbine airborne system-oriented multi-model fusion service state sensing method and device, and relates to the field of high-temperature equipment life management, and the method comprises the steps: designing a similar structural member, and carrying out the mechanical performance test; performing parameter fitting on the mechanical test data by using a multi-physical damage model in a fatigue-creep mutual combination manner; carrying out weight optimization and aggregation on the fitting result by adopting a multi-objective optimization method; mechanical test data is used as input, a physical damage model deviation factor is used as output, a classification task indicating whether the deviation factor is greater than 1 is used as correction of a deviation factor regression task, and a multi-task learning neural network is constructed and trained; and constructing a structural member service life prediction model by using the multi-physical damage model and the multi-task learning neural network, loading the structural member service life prediction model to an airborne system of the gas turbine, and performing local service life prediction on a to-be-tested part of the gas turbine. According to the invention, the accuracy and universality of life prediction of the to-be-tested part of the gas turbine are improved.

The invention belongs to the technical field of aviation airborne system design, and provides a helicopter airborne system-oriented novel software architecture and a construction method thereof, and the architecture comprises a hardware abstraction layer, a framework resource layer, an intelligent platform service layer and an application software layer from bottom to top. And the hardware abstraction layer realizes decoupling of hardware and basic software of an operating system. The framework resource layer supports operation of a hybrid key operating system, supports and isolates tasks and application programs with different key levels, software bases and computing power requirements, and provides basic computing communication resources and AI computing power resources. The intelligent platform service layer comprises middleware, a servitization function unit and a servitization management unit, and the servitization function unit comprises atomic services and enhanced services. And the application layer interacts with the intelligent platform service layer and is decoupled from a bottom software and hardware environment. The framework is suitable for unmanned / manned helicopters, and generalization of platform support and maximum reuse of software assets are achieved.

The invention relates to a fault simulation method suitable for engineering simulation of an electric vertical take-off and landing aircraft. The method comprises the following steps: injecting a target fault into a target simulation model of a to-be-tested electric vertical take-off and landing aircraft; controlling a target fault signal to carry out cross-system transmission on a plurality of target airborne systems of the to-be-tested electric vertical take-off and landing aircraft; wherein the target fault signal is a signal triggered based on a target fault; injection data of the target faults and operation data in the cross-system transmission process are obtained so as to be used for evaluating fault responses of the multiple target airborne systems. Through the method and the device, high-fidelity matching of fault injection and an actual fault response scene is realized, and the consistency of fault responses of a plurality of target airborne systems is optimized, so that the authenticity of fault simulation and the effectiveness of fault response evaluation of an electric vertical take-off and landing aircraft jig machine are improved, and the high-fidelity requirement of semi-physical simulation is met.

The invention discloses an aircraft performance monitoring method, device, terminal and system and a storage medium, and the method comprises the steps: obtaining a preprocessed flight data stream from an airborne flight data preprocessing device in the flight process of a target leg, analyzing and processing the flight data meeting the effective leg screening condition in the preprocessed flight data stream to obtain the flight data of the effective leg; based on the flight data of the effective leg, calling an embedded performance factor analysis logic to carry out performance factor analysis so as to obtain a performance factor of the effective leg; and in response to a flight end instruction of the target leg, displaying a performance monitoring result on a display based on the performance factor of each effective leg. According to the invention, while the timeliness of airplane performance monitoring is improved, the interference on airborne system data is avoided, the safety is ensured, and an airplane crew can master the performance condition of an airplane in time.

The invention relates to the field of unmanned aerial vehicle autonomous flight control and intelligent decision making, and discloses an unmanned aerial vehicle anti-disturbance flight system and method based on multi-source fusion perception. The system comprises an airborne system and a ground system, wherein the airborne system carries a visual, ultrasonic and inertial three-source module, a fusion calculation module in data connection with the three-source module, a robust control module in data connection with the fusion calculation module, and a degradation decision module in data connection with the fusion calculation module and the robust control module. The anti-disturbance capability of the operation of the unmanned aerial vehicle in the forest fire prevention process is improved, and reliable sensing support is provided for autonomous flight and task execution of the unmanned aerial vehicle.

The invention discloses a high-resolution SAR deception jamming signal rapid generation method and device, and belongs to the technical field of radar countermeasure. The method comprises the following steps: intercepting an SAR signal and measuring parameters of the SAR signal; obtaining a deception jamming template image, and carrying out edge optimization processing; performing two-dimensional partitioning on the template in the distance direction and the azimuth direction to obtain a plurality of sub-templates; calculating a phase compensation function for the central point of each sub-template, and carrying out phase optimization; the optimized sub-templates are superposed, and a high-quality product modulation matrix is generated; and multiplying the matrix by an intercepted SAR signal, and transmitting after digital-to-analog conversion and up-conversion to form a deception jamming signal. According to the method, through block phase compensation and template edge optimization, the imaging quality and concealment of the deception jamming image under the high-resolution SAR are remarkably improved, meanwhile, low calculation complexity is kept, and the method is suitable for satellite-borne and airborne SAR systems.

The application discloses a kind of line segment anti-aliasing parameter optimization method based on objective image quality evaluation under airborne display scene, for line segment anti-aliasing transition width FW Dependence artificial visual debugging, time-consuming, poor consistency, and fixed parameter is difficult to adapt to multi-line width, multi-resolution, arbitrary slope line segment Problem, reference Alpha matrix is generated using SSAA supersampling, PSNR is used as objective quantitative evaluation index to traverse optimization, and optimal FW parameter is obtained automatically and solidified to airborne system.The application can adapt to arbitrary slope and angle line segment rendering, edge smoothing, stable and reliable display effect, small amount of calculation, convenient for hardware implementation, can significantly improve the vector line segment rendering quality and consistency of airborne flat display, helmet display and other scenes, meet the application demand of airborne strong real-time, high reliability.

This invention discloses an automatic generation and evaluation method for airborne system signal monitoring voting strategies, comprising: Step 1, matching at least one pre-selected monitoring voting strategy from a monitoring voting algorithm simulation model library based on the attribute characteristics of the input signal; Step 2, evaluating whether the security of processing the input signal using the monitoring voting strategy meets the security target requirements of the voting value based on the signal availability data and signal integrity data of the input signal, and the matched monitoring voting strategy, thereby obtaining a recommended monitoring voting strategy; wherein, the monitoring voting algorithm simulation model library is pre-configured and includes multiple simulation models, with different simulation models representing different monitoring voting algorithms. The technical solution provided by this invention solves the problem that traditional monitoring voting strategies are no longer suitable for the rapid iteration and process assurance processes of civil aviation R&D.

The present invention belongs to the technical field of aviation airborne system safety analysis, and specifically relates to a method and system for generating FMES data for airborne system safety analysis. The method comprises: S1: acquiring FMEA data of the airborne system, performing data processing, and extracting data features using the BERT model; S2: using sinusoidal similarity to measure the FEMA structured data feature vectors and calculate the similarity of the FEMA structured data features; S3: obtaining the FEMA structured data feature similarity matrix and performing a first agglomerative hierarchical clustering analysis; S4: performing a second clustering analysis on the tree-like clusters of the FEMA structured data features based on fault tree analysis (FTA); and S5: generating structured Failure Mode and Effect Summary (FMES) data based on the second clustering results. The present invention proposes a complete framework for automatically generating FMES data, and improves the quality of the automatic generation through secondary clustering.

The invention relates to an avionics system optical fiber communication link health management technology, and provides an airborne communication link fault positioning method and system based on an embedded OFDR, and the method comprises the steps: integrating an embedded OFDR function unit in an airborne network switching module, outputting frequency linear scanning continuous wave test light, and dividing the test light into detection light and reference light; the detection light is sequentially injected into each to-be-detected optical fiber link through the switch exchange matrix, and returned backward Rayleigh scattering light is received and interferes with the reference light to generate a beat frequency signal; a Rayleigh scattering distance map is obtained through analog-to-digital conversion and fast Fourier transform and is compared with a pre-stored health reference map in a differential mode, an abnormal event is recognized, and the position of a fault point is accurately positioned. According to the method, on-line monitoring with sub-millimeter resolution and no blind area can be achieved under the conditions of low power and no communication interruption, multi-link automatic polling, fault link switching and maintenance information reporting are supported, and the requirements for high reliability and BIT autonomous diagnosis of an airborne system are met.

The invention belongs to the field of airborne system mode management, and particularly relates to an air-space platform airborne system mode management method. Comprising the following steps: after a system is normally powered off and powered on again, entering a normal starting mode; after the system is powered off abnormally in the air and powered on again, an air starting mode is entered; after executing DIF reset, the system enters a reset starting mode; after the system is started or the system receives a comprehensive control instruction, entering a control management mode, and executing comprehensive control and in-flight self-detection test; after the system receives the PBIT instruction, entering a system PBIT mode, and executing a self-detection test before the system flies; after receiving the MBIT instruction, the system enters a system MBIT mode and executes a system maintenance test; after receiving the OFP loading instruction, the system enters an OFP loading mode, and system software online loading is executed; after receiving the ground guarantee instruction, the system enters a ground guarantee mode and executes system ground guarantee; and after the power supply is powered off, entering a system power-off mode, and executing system power-off.

The invention discloses an aircraft airborne system architecture trade-off evaluation method and system based on ADCP, and belongs to the technical field of airborne system evaluation. The method comprises the following steps: selecting an ADCP four-dimensional index; defining primary / secondary index weights by adopting an analytic hierarchy process, and obtaining a comprehensive weight coefficient through consistency check; realizing index normalization transformation through a linear membership function; performing weighted summation to preliminarily screen an optimal framework; calculating physical parameters such as a system capability value and an efficiency value; and verifying whether the optimal architecture meets the condition that at least one core physical parameter is maximum or not, and if not, adjusting the weight or membership function. According to the method, the problems that existing evaluation indexes are disordered, weights are difficult to determine, physical significance is lacked and subjectivity is high are solved, scientificity, accuracy and engineering applicability of evaluation are improved, and the method is suitable for balancing various aircraft airborne system architectures.

The invention provides an airborne system modeling workload quantification method. The airborne system is divided into different levels, modeling workloads are continuously decomposed into modeling workloads of a part layer and modeling workloads of a middle layer (including the modeling workloads between a subsystem layer and a system layer, the modeling workloads between an equipment layer and the subsystem layer and the modeling workloads between the part layer and the equipment layer), and the modeling workloads of the middle layer and the modeling workloads of the part layer and the equipment layer are obtained by subdividing modeling objects. And the purpose of reducing the modeling difficulty is achieved.

The invention relates to a method for selecting a communication channel, called the usage channel, comprising: - a step of determining, for each channel, one or more items of information representative of a quality of transmission of a message, the message being either a so-called "useful" message received by the embedded system, or a probe message, called a "ping" message, - a step of classifying the channels according to indices representative of the transmission qualities, from said information, - a step of selecting the usage channel as being the channel, having the best transmission quality from said indices, - a step (101) of determining a buffering time for each useful message received, and if this time is non-zero, - a step (102) of transmitting the useful message, called the eligible useful message, instead of a probe message. Abstract figure: Figure 4

The application discloses an airborne control service comprehensive processing system supporting air-ground and air-air cooperative operation, and an airspace multi-state situation comprehensive module combines traffic data, weather data and terrain data with an executing local operation plan or an operation plan to be confirmed for supporting local temporary operation to generate comprehensive situation data; a local temporary control service operation plan generation module establishes an operation plan to be confirmed for supporting local temporary operation considering a potential conflict avoidance space-time region according to judgment on the comprehensive situation data, and outputs the operation plan to a local temporary control service operation plan negotiation module to negotiate with a ground control service system and an airborne system of another aircraft; and the application converts the executing local operation plan or regenerates the operation plan to be confirmed for supporting local temporary operation according to negotiation feedback information. The application can meet the comprehensive service capacity requirement of aircraft operation caused by future change of aviation operation mode.

The invention relates to a lightweight airborne visual tracking method and device based on random projection and a medium, belongs to the technical field of airborne computer vision and target tracking, and can reduce the calculation and storage cost of airborne platform feature processing, guarantee the target tracking precision and adapt to resource limited scenes. According to the invention, lightweight airborne visual tracking is realized based on locality sensitive hash (LSH) random projection, the method is suitable for resource-limited scenes of airborne platforms such as unmanned aerial vehicles and helicopters, and typical challenges such as target scale dramatic change, complex background interference and high-altitude high-angle shooting visual angle offset under airborne vision can be efficiently processed. The core requirements of an airborne system on low computing power occupation, low storage consumption and high real-time performance of a tracking algorithm are met; the LSH random projection technology is organically combined with an existing lightweight tracking architecture, on the premise that tracking precision is not remarkably lost, the calculation and storage cost of feature processing is further reduced, and the method becomes a constraint of breaking through airborne visual tracking resources-performance.

The embodiment of the invention provides a serial port communication filtering method and device based on an FPGA, computer equipment and a medium, and relates to the technical field of control systems.The serial port communication filtering method comprises the steps that serial port communication start bit filtering is carried out based on a first low level counter, a first high level counter and a first time counter; and performing serial port communication data bit, check bit and stop bit filtering based on the second low level counter, the second high level counter and the second time counter. The method comprises the following steps: detecting a falling edge at the beginning of data transmission, performing filtering detection on the falling edge and checking whether the falling edge is an interference signal when detecting that the falling edge exists in a serial port data bit, and receiving serial port communication data and performing filtering operation on a data bit, a check bit and a stop bit according to a filtering algorithm when a non-interference signal is a normal start bit. According to the scheme, the reliability and the stability of serial port communication among products of the airborne system are improved, hardware filtering is reduced, the adaptability of serial port data receiving is enhanced, and the development cost is reduced.

The invention belongs to the technical field of network testing, and particularly relates to a TTE network systematic testing method for an airborne system of an air-space platform. Comprising the following steps: checking network appearance; checking the effectiveness of the electrical characteristics of the network; checking the validity of the communication protocol; checking the effectiveness of switch communication; performing fault injection; and checking the flight state. According to the air-space platform airborne system TTE network systematic test method, TTE network conventional inspection items are covered, test flight requirements are met, meanwhile, the tail end of a development process to which test flight belongs is considered, and customized design is carried out on a communication protocol, fault injection and the like in combination with system characteristics, so that correctness and integrity of the TTE network before test flight are ensured.

The application provides an airplane system comprehensive test bench, and relates to the technical field of equipment testing; the application provides platform function support through simulation of a flight system, comprehensive control and test auxiliary systems, data acquisition and analysis systems, software test systems, airborne system integration modules and a fault injection system, and realizes linkage comprehensive experiments with different airplane system test benches through a platform I / O resource pool, a simulation power supply and distribution system, a test network, a reflective memory network and a wiring and junction system; the application realizes the erection of the airplane system comprehensive test bench between a power device system test bench, an atmospheric inertial navigation system test bench, a passenger cabin information system test bench, a copper bird test bench and an iron bird test bench, thereby meeting the linkage test operation requirements.

This invention discloses an airborne Wi-Fi system power amplifier assembly and design method. This design relates to the field of airborne Wi-Fi system power amplifiers. The assembly comprises a dual-band power amplifier module, which provides amplification for both the transmit and receive channels. The module includes a first path and a second path. The first path includes a radio frequency port TRX1, a radio frequency transmit / receive switch K‑0, a variable gain amplifier VGA‑1, a driver amplifier D1, a final amplifier A‑1, a unidirectional transmission circulator H1, a logic switch K‑2, a final amplifier A‑3, and an antenna port ANT1. This invention addresses the issues of low-quality and high power consumption associated with Wi-Fi signal coverage in specific environments within an airborne cabin.

The invention provides a performance testing device for dynamic impact mechanics of an aircraft cockpit airborne system. Comprising a floor, a console support group, a structural member connecting support group, a pedal simulation device, a cockpit console and instrument board, a cockpit seat fixing assembly, a seat assembly, a humanoid test model, a motion data acquisition assembly, a structural horizontal impact test bed and a control computer. The floor is fixed on the structure horizontal impact test bench; the pedal simulation device, the cockpit console and the instrument panel are fixed to the floor through the console support set. The seat assembly is fixed to a floor through the cockpit seat fixing assembly; structural members of the aircraft are fixed to the floor through the structural member connecting support set. The anthropomorphic test model is arranged on the seat assembly, and the motion data acquisition assembly is arranged on the periphery of the anthropomorphic test model. Through the performance testing device, the performance of dynamic impact mechanics of different forms and different types of cockpit airborne systems can be tested.

The invention relates to the field of airplane airborne system design, and discloses a Hypervisor-based cross-system adaptive communication architecture, method and equipment, a virtual machine monitor is introduced between two operating systems, so that the virtual machine monitor is located between the two operating systems, and the virtual machine monitor is responsible for managing hardware resources and providing a virtual operation environment for the two operating systems; according to the method, a virtual machine monitor is partitioned and placed in a shared memory area according to the type of cross-system data, and key real-time data can be preferentially transmitted without waiting for scheduling of a CPU (Central Processing Unit) by performing priority ranking on the data, so that the strict requirement of the aviation field on real-time performance is met; meanwhile, the division of the exclusive channel and the shared channel further optimizes the data transmission path. According to the invention, the data transmission speed can be effectively improved, and the time delay is reduced, so that the communication efficiency in the cross-system service process is improved.

1. Name of the designed product: Airborne communication antenna (5G AeroMACS). 2. Use of the designed product: used for the transmission and reception of radio frequency signals of the airborne 5G AeroMACS system. 3. Design points of the designed product: in shape. 4. Picture or photo best indicating the design points: perspective view.

The invention belongs to the technical field of aviation aircraft design, and particularly relates to a multi-mode power supply dual-redundancy cold standby type liquid cooling airborne system, method and medium, the system comprises liquid cooling pumps, a radiator, a power supply bus bar, time service equipment and a controller, the liquid cooling pumps comprise a liquid cooling pump 1 and a liquid cooling pump 2, inlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with liquid cooling electronic equipment, and inlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with the controller; outlets of the liquid cooling pump 1 and the liquid cooling pump 2 are connected with the radiator, the radiator is connected with the liquid cooling electronic equipment, the power supply bus bar comprises a power supply bus bar 1 and a power supply bus bar 2, the power supply bus bar 1 supplies power to the liquid cooling pump 1 through the circuit breaker 1, the power supply bus bar 2 supplies power to the liquid cooling pump 2 through the circuit breaker 2, and the power supply bus bar 1 and the power supply bus bar 2 are connected with the controller. The liquid cooling pump 1, the liquid cooling pump 2 and the liquid cooling electronic equipment are all connected with the controller; the time service equipment is connected with the controller; the system self-adaptive capability and task reliability of the dual-redundancy cold standby type environment control liquid cooling system in different power supply modes are improved, the heat dissipation requirement of the liquid cooling electronic equipment in a flight task is guaranteed as much as possible, and the system reliability of an aircraft when the different power supply modes are switched back and forth is guaranteed.

The invention discloses an airborne orbital angular momentum MDI-QKD link building device, which comprises a transmitting end Alice, a transmitting end Bob and a receiving end Charlie, and is characterized in that the transmitting end Alice comprises a first laser, a first spatial light modulator SLM1, a first attenuator ATT, a first reflector, a second reflector, a first intensity modulator IM and a first telescope; the Bob end comprises a second laser, a second spatial light modulator SLM2, a second attenuator, a third reflector, a fourth reflector, a second intensity modulator IM and a second telescope; the receiving end Charlie comprises a third telescope composed of a fifth lens and a sixth lens, a fourth telescope composed of a seventh lens and an eighth lens, first to third beam splitters BS, first and second polarization gratings PG, fifth to eighth reflectors, first to fourth mode sorters MS, and first to fourth detectors. The invention further provides an MDI-QKD performance improvement method of the unmanned aerial vehicle platform OAM code based on the grey wolf-differential evolution hybrid algorithm GWO-DE. According to the method, an efficient parameter optimization strategy is provided for an airborne OAM-MDI-QKD system of a fixed link, a data set obtaining scheme for machine learning prediction is provided for meeting the high real-time requirement of a mobile link, and an idea is provided for achieving a safer and more reliable quantum communication network in the future.

A directional antenna system configured to be installed in an Unmanned Airborne System (UAS) includes an antenna array including one or more directional antennas and a control system. Each antenna is configured to transmit signals into a predetermined outgoing directional beam and to receive signals coming along a predetermined incoming directional beam. The antennas are arranged in a two-dimensional structure or a three-dimensional structure. The antenna array is connected to the UAS. The control system configured to supply signals to the antennas of the antenna array and to receive signals from antennas of the antenna array and to exchange signals with the UAS mission equipment. The antenna array includes one or more antenna elements made of a material suitable for additive manufacturing.

The invention relates to the technical field of airborne system hardware abstraction, and discloses a hardware abstraction method and system for an airborne system, computer equipment and a medium, and the method comprises the steps: abstracting each physical equipment in the airborne system from different types of physical equipment into abstract equipment with the same interface, shielding the physical difference between different types of equipment, and improving the hardware abstraction efficiency. And forming the same abstract device with the same function. And meanwhile, analyzing and counting the interfaces of different types of physical equipment of each type of physical equipment to form a group of uniform interfaces of the abstract equipment. For the upper software, the method shields the physical difference of different hardware of different manufacturers, obviously improves the development efficiency and cross-platform portability of the upper software, and facilitates the development and transplantation of the upper software; for manufacturers, the method unifies the interface requirements of different models of aircrafts, and facilitates formation of lineage design and research and development of products with unified functions and different performances.

The embodiment of the application discloses a power supply configuration architecture of a redundant airborne system, wherein at least four redundant devices are included in the redundant airborne system, a power supply system includes at least two power supply subsystems and professional accumulators, each power supply subsystem has two power supply bus bars, including a main bus bar and an emergency bus bar; the power supply configuration architecture includes: two devices in the power supply configuration architecture are connected with the professional accumulators respectively, one of the two devices is connected with one power supply bus bar in one power supply subsystem, and the other device is connected with one power supply bus bar in the other power supply subsystem; the other two devices are connected with the main bus bar in one power supply subsystem and the emergency bus bar in the other power supply subsystem respectively. The technical scheme provided by the embodiment of the application solves the problem that the existing power supply configuration scheme of the redundant airborne system is difficult to have both the power supply common-mode fault mitigation requirement and the high task reliability level.

The invention relates to the technical field of helicopter maintenance and detection, in particular to a multifunctional maintenance and detection device and method for a helicopter, and the device comprises a housing, the housing is internally provided with a test circuit, and the test circuit at least loads a function inspection loop and an explosion cap simulation loop; through a load function inspection loop and a configured memory indication function, maintenance detection can be effectively carried out on a power supply line of a helicopter airborne system, and the problem that communication between maintenance engineers is difficult during regional inspection is solved. Meanwhile, the explosion cap simulation loop can effectively avoid the risk that a fire extinguishing bottle explosion cap, a buoy gas cylinder explosion cap and a cabin door explosion connecting rod explosion cap are mistakenly detonated in the testing process, the maintenance and detection efficiency of the helicopter is improved, and the corresponding risk is reduced.